Hole effects on lateral buckling of laminated cantilever beams

Eryiğit, Ersin; Zor, Mehmet; Arman, Yusuf

doi:10.1016/j.compositesb.2008.07.005

Cited by 23 publications

(15 citation statements)

References 22 publications

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“…An identical trend between Pm and K could be expected under these circumstances, since the value of Pm for structures under pure compression typically corresponds to the initiation of global buckling, which is determined by their stiffness [60,61] ence Pm. In fact, Eryigit et al [29] reported on the buckling loads of thin glass-epoxy laminates with a circular hole at different locations, among which equally to this work, i.e., at the middle of the laminate. For this geometry, the buckling load significantly diminished by increasing the length between grips.…”

Section: Summary Of the Resultsmentioning

confidence: 99%

“…At a certain level of applied load, elastic instability of the beam leads to its transverse deflec-tion accompanied by crosssectional rotation around the axis of smaller second moment of inertia, which grows at an approximate constant load. This phenomenon is known as lateral buckling, and the corresponding load as the buckling load [29]. Owing to these mechanisms, fibre-reinforced laminates sustain smaller loads in compression than tension [30,31], implying that composite struc-tures under bending are more likely to fail in the compression re-gions.…”

Section: Introductionmentioning

confidence: 99%

“…The compressive behaviour of composite structures must also be considered in the design stages. In fact, different mechanisms arise under compression, such as fibres microbuckling, for buckling of restrained structures [25][26][27][28], or global buckling of the assembly between clamping points, if no transverse restriction exists [29]. Fibres microbuckling comes from the compliant materials used as matrix, whilst global buck-ling is justified by the slenderness of elements, largely depending on their crosssection and elastic properties, in addition to the im-posed boundary and loading conditions.…”

Section: Introductionmentioning

confidence: 99%

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Buckling strength of adhesively-bonded single and double-strap repairs on carbon-epoxy structures

Campilho

Moura

Ramantani

et al. 2010

Composites Science and Technology

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This work reports on an experimental and finite element method (FEM) parametric study of adhesively-bonded single and double-strap repairs on carbon-epoxy structures under buckling unrestrained com-pression. The influence of the overlap length and patch thickness was evaluated. This loading gains a par-ticular significance from the additional characteristic mechanisms of structures under compression, such as fibres microbuckling, for buckling restrained structures, or global buckling of the assembly, if no trans-verse restriction exists. The FEM analysis is based on the use of cohesive elements including mixed-mode criteria to simulate a cohesive fracture of the adhesive layer. Trapezoidal laws in pure modes I and II were used to account for the ductility of most structural adhesives. These laws were estimated for the adhesive used from double cantilever beam (DCB) and end-notched flexure (ENF) tests, respectively, using an inverse technique. The pure mode III cohesive law was equalled to the pure mode II one. Compression failure in the laminates was predicted using a stress-based criterion. The accurate FEM predictions open a good prospect for the reduction of the extensive experimentation in the design of carbon-epoxy repairs. Design principles were also established for these repairs under buckling.

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Section: Summary Of the Resultsmentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

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Buckling strength of adhesively-bonded single and double-strap repairs on carbon-epoxy structures

Campilho

Moura

Ramantani

et al. 2010

Composites Science and Technology

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“…The effects of hole diameter and hole location on the lateral buckling behaviour of woven fabric laminated composite cantilever beams were investigated by Eryigit et al [14]. Pasinli [15] studied the similar cantilever beams but having two square or two circular holes by using theoretical, experimental and numerical methods.…”

Section: Introductionmentioning

confidence: 99%

Buckling and post-buckling of a composite C-section with cutout and flange reinforcement

Guo

Zhang

et al. 2014

Composites Part B: Engineering

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a b s t r a c tThis paper presents an investigation into the effect of cutout and flange reinforcement on the buckling and post-buckling behaviour of a carbon/epoxy composite C-section structure. The C-section having a cutout in the web is clamped at one end and subjected to a shear load at the other free end. Three different stiffener reinforcements were investigated in finite element analysis by using MSC Nastran. Buckling load was predicted by using both linear and nonlinear FE analysis. Experiments were carried out to validate the numerical model and results. Subsequently post-buckling analysis was carried out by predicting the load-deflection response of the C-section beam in nonlinear analysis. Tsai-Wu failure criterion was used to detect the first-play-failure load. The effect of circular and diamond cutout shape and effective flange reinforcements were investigated. The results show that the cutout and reinforcement have little effect on the buckling stability. However an L-shape stiffener to reinforce the C-section flange can improve the critical failure load by 20.9%.

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“…Dokuma kumaş tabakalı kompozit konsol kirişin yanal burkulması üzerine kiriş üzerinde bulunan deliklerin etkisi deneysel bir çalışma ile incelenmiştir [11]…”

Section: Introductionunclassified

İnce Cidarlı Kompozit Kirişlerin Yanal Burkulma Davranışına Şerit Delaminasyonun Etkisi

Arman¹

2019

deufmd

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Öz Bu çalışmada, şerit halinde süreksizlik bölgesine (delaminasyona) sahip kompozit konsol kirişlerin yanal burkulma yükleri deneysel olarak ve sonlu elemanlar yöntemi kullanılarak elde edilmiştir. Deneylerde kullanılacak kompozit numunelerin çıkarıldığı levhalar vakum destekli reçine infüzyonu yöntemi ile tek yönlü fiber kumaşlar kullanılarak üretilmiştir. Sekiz tabaka kullanılan levhalarda fiber yönlenme açıları üç farklı açıda [(0˚/90˚)2]s, [(30˚/-60)2]s ve [(45˚/-45˚)2]s olarak seçilmiştir. Numuneler bir ucu ankastre diğer ucu serbest olacak şekilde mesnetlenmiş ve uygulanan basma testi sonucunda kritik yanal burkulma yükleri elde edilmiştir. Sonlu elemanlar analizlerinde ANSYS 19.1 paket programı kullanılmıştır. Çalışma sonucunda (30˚/-60) ve (45˚/-45˚) fiber yönlenme açılarına sahip kirişlerin kritik yanal burkulma yüklerinin, (0˚/90˚) fiber yönlenme açısına sahip kirişlere göre daha yüksek olduğu gözlenmiştir. Bunun yanında delaminasyon yüksekliğinin artması da kritik yanal burkulma yüklerinin azalmasına sebep olmuştur. Ayrıca test sonuçları ve sonlu elemanlar analiz sonuçları karşılaştırılmış ve birbirine yakın değerler elde edilmiştir.

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Hole effects on lateral buckling of laminated cantilever beams

Cited by 23 publications

References 22 publications

Buckling strength of adhesively-bonded single and double-strap repairs on carbon-epoxy structures

Buckling strength of adhesively-bonded single and double-strap repairs on carbon-epoxy structures

Buckling and post-buckling of a composite C-section with cutout and flange reinforcement

İnce Cidarlı Kompozit Kirişlerin Yanal Burkulma Davranışına Şerit Delaminasyonun Etkisi

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